ATTITUDE CONTROL OF MULTIPLE RIGID BODY SPACECRAFT WITH FLEXIBLE HINGE JOINTS

Control algorithm is developed for a satellite with flexible appendages to achieve a good pointing performance. Detailed modeling activity was carried out that consists of sensor and actuator models, disturbances and system dynamics. Common hardware found in the spacecraft such as reaction wheels, gyroscopes, star trackers etc. were included in the model. Furthermore, the Newton-Euler method is employed for the derivation of multi-body equations of motion. Proper metrics such as accuracy, jitter and stability are used to evaluate the pointing performance of two control schemes: quaternion feedback controller, and linear quadratic regulator. Simulation results are given and discussed